N5470W Weight and Balance Sheet
Piper PA-28 Cherokee 160 · Weight And Balance
Overview
This document is a Weight and Balance Sheet for the Piper PA-28 Cherokee 160, specifically for the aircraft with registration N5470W. It provides essential data regarding the weight distribution and balance of the aircraft, which is critical for safe flight operations. The document includes the basic empty weight, arm, and moment calculations necessary for determining the aircraft's weight limits and balance during various phases of flight. Pilots and operators can use this information to ensure that the aircraft is loaded within safe limits before takeoff, which is vital for performance and safety.
- Basic Empty Weight: 1259.1 lbs
- Arm: 88.15 inches
- Moment: 110987.56
- Preflight calculations for pressure altitude and density altitude are essential for performance assessment.
- Ensure all weight calculations (pilot, passengers, baggage) are within limits before flight.
Document
Source
Originally published by thomas-anderson-oaro.squarespace.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Weight And Balance
- Year
- 2017
- Pages
- 1
- File size
- 76 KB
- Publisher
- thomas-anderson-oaro.squarespace.com
Most owners only have the POH. Here's the essential set for the Piper PA-28 Cherokee 160.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
More Piper PA-28 Cherokee 160manuals & documents
- Piper PA-28 Cherokee Systems DescriptionSystems Description
- 50 HOUR PROGRESSIVE INSPECTION MANUALService Manual
- SCHEDULE OF AIRWORTHINESS DIRECTIVESAirworthiness Directives
- PIPER PA-28 STRAIGHT WING MODEL GAP SEALS STC No. SA603GLSupplemental Type Certificate
- SCHEDULE OF AIRWORTHINESS DIRECTIVESAirworthiness Directives
- Airplane Flight Manual for the Piper PA-28 Cherokee 160Flight Manual
- Performance Data for the Piper PA-28 Cherokee 160Performance Data
In this document
Weight and Balance Data
The Weight and Balance Sheet lists the Basic Empty Weight of the Piper PA-28 Cherokee 160 as 1259.1 lbs, with an arm of 88.15 inches and a moment of 110987.56. Additional sections are provided for pilot and passenger weights, rear passenger(s), rear baggage area, zero fuel weight, ramp fuel, and ramp weight, which are essential for calculating the total weight and balance of the aircraft.
Preflight Information
The document includes a section for preflight information, which covers critical data such as weather conditions, runway details, wind, visibility, temperature, dewpoint, and altimeter settings. This information is crucial for pilots to assess the flight environment and make informed decisions regarding takeoff and landing distances.
Altitude Calculations
It provides formulas for calculating pressure altitude and density altitude, which are important for understanding aircraft performance. Pressure altitude is calculated by taking the standard pressure minus the current pressure setting, multiplied by 1,000, plus the field elevation. Density altitude is derived from pressure altitude plus a correction factor based on outside air temperature.
Safety notes
- Always verify weight and balance calculations before flight to ensure safety.
- Monitor fuel burn to maintain awareness of landing weight.
Full document text
June 14, 2017 (Revision 1) N5470W Weight and Balance Sheet Piper PA28-160 Weight (lbs.) Arm Moment Basic Empty Weight 1259.1 88.15 110987.56 Pilot and Passenger Rear Passenger(s) Rear Baggage Area Zero Fuel Weight Ramp Fuel Ramp Weight Start/Taxi/Run-Up Fuel Takeoff Weight Fuel Burn Landing Weight 91.103 Preflight Information Weather Runway Wind Length Visibility T/O Ground Roll Temp/Dewpoint T/O Distance (50ft) Altimeter LND Ground Roll Remarks LND Distance (50ft) Pressure Altitude Density Altitude *Pressure altitude = (standard pressure - your current pressure setting) x 1,000 + field elevation *Density altitude = pressure altitude + [120 x (OAT - ISA Temp)] ISA at sea level is 15 degrees C. 0 200 400 600 800 1000 1200 1400 1600 1800 2000 2200 2400 82 84 86 88 90 92 94 96 98